CN115436009A - Nozzle thrust measurement test system with integrated rear body and nozzle - Google Patents
Nozzle thrust measurement test system with integrated rear body and nozzle Download PDFInfo
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- CN115436009A CN115436009A CN202211388071.4A CN202211388071A CN115436009A CN 115436009 A CN115436009 A CN 115436009A CN 202211388071 A CN202211388071 A CN 202211388071A CN 115436009 A CN115436009 A CN 115436009A
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- support rod
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- pipe
- spray pipe
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0028—Force sensors associated with force applying means
- G01L5/0038—Force sensors associated with force applying means applying a pushing force
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention belongs to the technical field of thrust vector control of aircrafts, and discloses a jet pipe thrust measurement test system with a rear body and a jet pipe integrally designed. The ventilating support rod of the jet pipe thrust measurement test system is a circular pipe body, the front end head is closed, a fairing and a rear end opening are installed; the front end of the ventilation support rod is circumferentially provided with ventilation blades which are arranged in an axisymmetric manner; the rear end of the ventilating strut is sequentially connected with the measuring section, the aircraft afterbody and the spray pipe; the measuring section comprises a ring balance and a corrugated pipe which are sleeved in sequence from outside to inside; the central axis of the nozzle and the central axis of the vent strut have a nozzle deflection angle alpha. The test system for measuring the thrust of the spray pipe measures the stress of the spray pipe under the condition of truly simulating the turbulent flow of the rear body of the airplane body, can directly measure the data of 'spray pipe thrust-reducing-spray pipe resistance' of the spray pipe, improves the authenticity and reliability of the data, simplifies the later data processing process, is favorable for reducing the technical risk and research and development cost of the integrated design of the flying and launching and shortens the development period of an airplane engine.
Description
Technical Field
The invention belongs to the technical field of thrust vector control of aircrafts, and particularly relates to a jet pipe thrust measurement test system with a rear body and a jet pipe integrally designed.
Background
The thrust vector control technology is a technology that uses a part of the engine thrust directly for the control of the flight control of an aircraft through jet flow steering of a nozzle. The aircraft as a whole has the mutual influence and inseparability of the external circumfluence of the aircraft body and the internal fluence of the propulsion system. The inner flow is captured by the air inlet, and returns to the outer flow after the air inlet decelerates and expands pressure, the engine burns and increases pressure and the jet pipe accelerates and reduces pressure. This process generates a series of complex flow coupling interference phenomena, which cause coordination and matching problems among the air intake duct, the engine, the nozzle, and the Airframe, i.e., a Propulsion-Airframe Integration problem, and directly affect the aerodynamic, propulsion, maneuvering, and safety performance of the aircraft. The maximization of the internal and external flow pneumatic comprehensive benefits can be realized only by fully recognizing the flow coupling interference characteristics among the engine body/air inlet channel, the air inlet channel/engine and the spray pipe/engine body and clarifying the action rules and the influence characteristics of the engine body/air inlet channel/engine and the spray pipe/engine body, so that the compatibility of a propulsion system and the engine body is ensured, and the design target is reached. Among these, for the nozzle, in order to evaluate the thrust efficiency of the air jet engine exhaust under outflow conditions, it is necessary to measure the effective thrust of the nozzle, which is the most interesting indicator. The thrust characteristic of the nozzle is equal to the sum of the thrust of the nozzle (positive value) and the resistance acting on the nozzle shell (negative value), namely the thrust of the nozzle-the reduction-the resistance of the nozzle.
Usually, aircraft thrust vectoring nozzle characteristic data adopts afterbody support or belly/back support mode, in order to record individual nozzle thrust, test model usually adopts two-layer nested method, separate interior nozzle and outside fuselage casing, must keep enough clearance between two-layer and prevent to collide with each other, lead to the outside stream of organism and propulsion system internal flow to influence each other simulation distortion, and the internal cavity pressure between two-layer is difficult to survey accurately, the measured data is the nozzle thrust that does not deduct the resistance data, need can obtain the nozzle characteristic parameter of this real concern of "nozzle thrust-subtract-nozzle resistance" through a series of revisions.
Currently, a nozzle thrust measurement test system with a rear body and a nozzle integrated design needs to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a test system for measuring thrust of a spray pipe, which is integrally designed by a rear body and the spray pipe.
The invention relates to a jet pipe thrust measurement test system with an integrally designed afterbody and jet pipe, which is characterized by comprising a ventilating blade, a ventilating support rod, a ring balance, an aircraft afterbody, a jet pipe, a fairing and a corrugated pipe;
the ventilation supporting rod is a circular tube body I, the front end of the ventilation supporting rod is closed, and the rear end of the ventilation supporting rod is opened;
a fairing is arranged on the end head of the front end of the ventilating strut; the circumferential direction of the front end of the ventilating support rod is provided with ventilating blades which are distributed in an axisymmetric way;
the rear end of the ventilating support rod is sequentially connected with the measuring section, the aircraft rear body and the spray pipe, the aircraft rear body is a circular pipe body II, and the spray pipe is an axisymmetric spray pipe; the measuring section comprises a ring balance and a corrugated pipe which are sleeved in sequence from outside to inside, the fixed end of the ring balance is arranged on the outer layer installation surface at the rear end of the ventilating support rod, the free end of the ring balance is arranged on the outer layer installation surface at the front end of the rear body of the aircraft, the front end of the corrugated pipe is arranged on the inner layer installation surface at the rear end of the ventilating support rod, and the rear end of the corrugated pipe is arranged on the inner layer installation surface at the front end of the rear body of the aircraft;
the central axes of the fairing, the ventilating blade, the ventilating support rod, the annular balance, the aircraft rear body and the corrugated pipe are superposed with the central axis of the wind tunnel test section; the central axis of the spray pipe and the central axis of the wind tunnel test section form an included angle alpha, and the alpha is a spray pipe deflection angle;
a plurality of blade airflow channels communicated with an external high-pressure air source are arranged inside the ventilation blade, airflow outlets of the blade airflow channels are positioned on the inner wall of the ventilation support rod, and a ventilation support rod airflow channel is arranged on the central axis of the ventilation support rod; the high-pressure air source airflow enters the airflow channel of the ventilating support rod through the airflow outlet along the blade airflow channel and then is sprayed out through the corrugated pipe and the spray pipe; the ring balance measures aerodynamic force and aerodynamic moment of the spray pipe; the corrugated pipe deforms along with the ring balance, and high-pressure air source airflow in the airflow channel of the ventilation support rod is sealed and isolated, so that the influence of the high-pressure air source airflow on the measurement of the ring balance is avoided; the pressure range of the high-pressure air source is 5MPa to 8MPa.
Furthermore, the deflection angle alpha of the jet pipe ranges from minus 20 degrees to 20 degrees.
Furthermore, the windward side of the ventilating vane is provided with an arc windward side for rectification.
Furthermore, the front end of the ventilation support rod is closed by a blocking cover; the blocking cover is a stepped cylinder, and the diameter of the front section cylinder of the blocking cover is smaller than that of the rear section cylinder; the rear section of the cylinder of the blocking cover is inserted into the front end of the ventilation support rod; the front section cylinder of the blocking cover extends out of the ventilating support rod, and the clamping sleeve is sleeved on the front section cylinder of the blocking cover; the rear end of the cutting sleeve is provided with a circular groove matched with the front end head of the ventilation support rod, the rear end face of the cutting sleeve is a contact face of the cutting sleeve and the front end face of the ventilation blade, and the front end of the cutting sleeve is provided with a locking nut; screwing the locking nut, tightly pushing the front end face of the ventilating blade by the clamping sleeve, and fixing the blocking cover and the clamping sleeve;
the fairing is sleeved on the clamping sleeve and wraps the blocking cover, the locking nut and the clamping sleeve, and the spherical outer surface of the fairing faces to incoming flow and is used for incoming flow rectification.
Furthermore, a sealing ring I is arranged on the inner wall of the cutting sleeve and used for sealing the contact surface of the cutting sleeve and the front section cylinder of the blocking cover; the rear end face of the clamping sleeve is provided with a sealing ring II for sealing the contact surface of the rear end face of the clamping sleeve and the front end face of the ventilation blade; a sealing ring III is arranged on the rear section of the cylinder of the blocking cover and used for sealing the contact surface of the blocking cover and the inner wall of the ventilating support rod; a sealing ring IV is arranged at the front section of the ventilation support rod and used for sealing the contact surface of the ventilation support rod and the rear end surface of the ventilation blade; the front end of the corrugated pipe is provided with a sealing ring V for sealing the contact surface between the inner layer mounting surface at the rear end of the ventilating support rod and the front end of the corrugated pipe, and the front end of the corrugated pipe is also provided with a sealing ring V for sealing the contact surface between the inner layer mounting surface at the front end of the rear body of the aircraft and the rear end of the corrugated pipe.
The invention relates to a nozzle thrust measurement test system with a rear body and a nozzle integrated design, which simplifies an aircraft model obtained by scaling an aircraft, removes the head of the aircraft model, designs the rear section of the aircraft model and a vent strut into a whole, and finally adopts a circular tube body of the vent strut as the aircraft model. In the test process, parameters such as the flying speed, the height and the like of the aircraft are simulated by the incoming flow of the wind tunnel, and the incoming flow of the airflow is parallel to the central axis of the ventilating strut. Meanwhile, the deflection angle alpha of the spray pipe is changed to realize the turning jet flow of the spray pipe, and the spray pipe becomes a vector spray pipe; the high-pressure air source airflow enters the airflow channel of the ventilating support rod along the blade airflow channel, and is sprayed out through the corrugated pipe, the aircraft afterbody and the spray pipe to simulate the jet flow of the vectoring spray pipe. The corrugated pipe has the functions of ventilation but does not transmit force and moment, and does not influence the aerodynamic force and aerodynamic moment of the measuring nozzle of the ring balance.
In summary, the jet pipe thrust measurement test system with the integrally designed afterbody and jet pipe adopts a head support mode, integrally designs an external machine body and a tail jet pipe model, utilizes bellows seal to realize ventilation and force transmission prevention, measures the stress of the jet pipe under the condition of truly simulating the disturbed flow of the afterbody of the machine body, can directly measure the target data of jet pipe thrust-reduction-jet pipe resistance of the jet pipe, improves the authenticity and reliability of the data, simplifies the process of later data processing, is favorable for reducing the technical risk and research and development cost of the integrated flight and launch design, and shortens the development period of an aircraft engine.
Drawings
FIG. 1 is a schematic structural diagram (perspective view) of a nozzle thrust measurement test system with a rear body and a nozzle integrally designed according to the present invention;
FIG. 2 is a schematic structural diagram (sectional view) of a nozzle thrust measurement test system with an integrated rear body and nozzle design according to the present invention;
FIG. 3 is a schematic structural view (cross-sectional view) of a vent strut head fairing in a nozzle thrust measurement test system with integrated design of a afterbody and a nozzle of the invention;
FIG. 4 is a schematic view (cross section) of the nozzle deflection angle in the nozzle thrust measurement test system with the integrated design of the afterbody and the nozzle.
In the figure, 1, a gas collecting chamber; 2. a ventilation blade; 3. a ventilation strut; 4. a ring balance; 5. an aircraft aft body; 6. a nozzle; 7. a cowling; 8. blocking the cover; 9. locking the nut; 10. a ferrule; 11. a sealing ring I; 12. a sealing ring II; 13. a sealing ring III; 14. a sealing ring IV; 15. a sealing ring V; 16. a vane airflow passage; 17. an airflow outlet; 18. a vent strut airflow channel; 19. a high pressure gas pipe inlet; 20. a bellows.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
The invention relates to a nozzle thrust measurement test system with integrally designed afterbody and nozzle, which comprises a ventilating blade 2, a ventilating support rod 3, a ring balance 4, an aircraft afterbody 5, a nozzle 6, a fairing 7 and a corrugated pipe 20;
the ventilation support rod 3 is a circular tube body I, the front end of the ventilation support rod 3 is closed, and the rear end of the ventilation support rod is open;
a fairing 7 is arranged on the end head of the front end of the ventilating support rod 3; the circumferential direction of the front end of the ventilating support rod 3 is provided with ventilating blades 2 which are distributed in an axisymmetric way;
the rear end of the ventilating support rod 3 is sequentially connected with a measuring section, an aircraft rear body 5 and a spray pipe 6, the aircraft rear body 5 is a circular pipe body II, and the spray pipe 6 is an axisymmetric spray pipe; the measuring section comprises a ring balance 4 and a corrugated pipe 20 which are sleeved in sequence from outside to inside, the fixed end of the ring balance 4 is arranged on the outer layer installation surface at the rear end of the ventilating support rod 3, the free end of the ring balance 4 is arranged on the outer layer installation surface at the front end of the rear body 5 of the aircraft, the front end of the corrugated pipe 20 is arranged on the inner layer installation surface at the rear end of the ventilating support rod 3, and the rear end of the corrugated pipe 20 is arranged on the inner layer installation surface at the front end of the rear body 5 of the aircraft;
the central axes of the fairing 7, the ventilating blade 2, the ventilating support rod 3, the ring balance 4, the aircraft rear body 5 and the corrugated pipe 20 are coincided with the central axis of the wind tunnel test section; an included angle alpha is formed between the central axis of the spray pipe 6 and the central axis of the wind tunnel test section, and alpha is a spray pipe deflection angle;
a plurality of blade airflow channels 16 communicated with an external high-pressure air source are arranged inside the ventilation blade 2, airflow outlets 17 of the blade airflow channels 16 are positioned on the inner wall of the ventilation support rod 3, and a ventilation support rod airflow channel 18 is arranged on the central axis of the ventilation support rod 3; high-pressure air source airflow enters the ventilating support rod airflow channel 18 along the blade airflow channel 16 through the airflow outlet 17 and then is sprayed out through the corrugated pipe 20 and the spray pipe 6; the ring balance 4 measures aerodynamic force and aerodynamic moment of the spray pipe 6; the corrugated pipe 20 deforms along with the ring balance 4 and seals and isolates the high-pressure air source airflow in the airflow channel 18 of the ventilating strut, so that the high-pressure air source airflow is prevented from influencing the measurement of the ring balance 4; the pressure range of the high-pressure air source is 5MPa to 8MPa.
Furthermore, the deflection angle alpha of the nozzle ranges from minus 20 degrees to 20 degrees.
Further, the windward side of the ventilating vane 2 is provided with an arc windward side for rectification.
Further, the front end of the ventilation strut 3 is closed by a plug cover 8; the blocking cover 8 is a step cylinder, and the diameter of the front section cylinder of the blocking cover 8 is smaller than that of the rear section cylinder; the rear section of the cylinder of the blocking cover 8 is inserted into the front end of the ventilation support rod 3; the front section cylinder of the blocking cover 8 extends out of the ventilating support rod 3, and the cutting sleeve 10 is sleeved on the front section cylinder of the blocking cover 8; the rear end of the cutting sleeve 10 is provided with a circular groove matched with the front end head of the ventilation support rod 3, the rear end face of the cutting sleeve 10 is a contact face of the cutting sleeve 10 and the front end face of the ventilation blade 2, and the front end of the cutting sleeve 10 is provided with a locking nut 9; the locking nut 9 is screwed down, the clamping sleeve 10 props against the front end face of the ventilating vane 2, and the blocking cover 8 and the clamping sleeve 10 are fixed;
the fairing 7 is sleeved on the clamping sleeve 10 and wraps the blocking cover 8, the locking nut 9 and the clamping sleeve 10, and the spherical outer surface of the fairing 7 faces the incoming flow and is used for incoming flow rectification.
Further, a sealing ring I11 is arranged on the inner wall of the cutting sleeve 10 and used for sealing the contact surface of the cutting sleeve 10 and the front section cylinder of the blocking cover 8; the rear end face of the cutting sleeve 10 is provided with a sealing ring II 12 for sealing the contact surface of the rear end face of the cutting sleeve 10 and the front end face of the ventilating blade 2; a sealing ring III 13 is arranged on the rear section of the cylinder of the blocking cover 8 and used for sealing the contact surface of the blocking cover 8 and the inner wall of the ventilating support rod 3; a sealing ring IV 14 is arranged at the front section of the ventilation support rod 3 and used for sealing the contact surface of the ventilation support rod 3 and the rear end surface of the ventilation blade 2; the front end of the corrugated pipe 20 is provided with a sealing ring V15 for sealing the contact surface between the inner layer installation surface at the rear end of the ventilation strut 3 and the front end of the corrugated pipe 20, and the front end of the corrugated pipe 20 is also provided with a sealing ring V15 for sealing the contact surface between the inner layer installation surface at the front end of the aircraft rear body 5 and the rear end of the corrugated pipe 20.
Example 1
As shown in fig. 1 to 4, the nozzle thrust measurement test system integrally designed by the afterbody and the nozzle of the embodiment is applied to a high-speed free jet wind tunnel, the nozzle thrust measurement test system is installed at a wind tunnel nozzle outlet of the high-speed free jet wind tunnel, the ventilating blade 2, the ventilating support rod 3, the ring balance 4, the aircraft afterbody 5, the bellows 20, the nozzle 6 and the fairing 7 are located in a wind tunnel test section, wherein a space outside the ventilating blade 2 is an air collection chamber 1 of the high-speed free jet wind tunnel, and an airflow pipeline of a high-pressure air source enters the air collection chamber 1 through a high-pressure air pipe inlet 19 of the air collection chamber 1 and is fixedly connected with an interface of the blade airflow channel 16.
Although the embodiments of the present invention have been disclosed above, it is not limited to the applications listed in the description and the embodiments, and it can be fully applied to various fields of high-speed free jet pressure matching pattern methods suitable for the present invention. It will be apparent to those skilled in the art that additional modifications and adaptations can be readily made without departing from the principles of the invention, and the invention is not limited to the specific details and illustrations set forth herein.
Claims (5)
1. A nozzle thrust measurement test system with a rear body and a nozzle integrally designed is characterized by comprising ventilating blades (2), a ventilating support rod (3), a ring balance (4), an aircraft rear body (5), a nozzle (6), a fairing (7) and a corrugated pipe (20);
the ventilation support rod (3) is a circular tube body I, the front end of the ventilation support rod (3) is closed, and the rear end of the ventilation support rod is opened;
a fairing (7) is arranged on the end head of the front end of the ventilating support rod (3); the circumferential direction of the front end of the ventilating support rod (3) is provided with ventilating blades (2) which are distributed in an axisymmetric way;
the rear end of the ventilating support rod (3) is sequentially connected with the measuring section, the aircraft rear body (5) and the spray pipe (6), the aircraft rear body (5) is a circular pipe body II, and the spray pipe (6) is an axisymmetric spray pipe; the measuring section comprises a ring balance (4) and a corrugated pipe (20) which are sleeved in sequence from outside to inside, the fixed end of the ring balance (4) is installed on the outer layer installation surface of the rear end of the ventilating support rod (3), the free end of the ring balance (4) is installed on the outer layer installation surface of the front end of the rear body (5) of the aircraft, the front end of the corrugated pipe (20) is installed on the inner layer installation surface of the rear end of the ventilating support rod (3), and the rear end of the corrugated pipe (20) is installed on the inner layer installation surface of the front end of the rear body (5) of the aircraft;
the central axes of the fairing (7), the ventilating blade (2), the ventilating support rod (3), the ring balance (4), the aircraft rear body (5) and the corrugated pipe (20) are superposed with the central axis of the wind tunnel test section; an included angle alpha is formed between the central axis of the spray pipe (6) and the central axis of the wind tunnel test section, and alpha is a spray pipe deflection angle;
a plurality of blade airflow channels (16) communicated with an external high-pressure air source are arranged in the ventilating blade (2), airflow outlets (17) of the blade airflow channels (16) are positioned on the inner wall of the ventilating support rod (3), and a ventilating support rod airflow channel (18) is arranged on the central axis of the ventilating support rod (3); airflow of a high-pressure air source enters an airflow channel (18) of the ventilating support rod through an airflow outlet (17) along an airflow channel (16) of the blade and then is sprayed out through a corrugated pipe (20) and a spray pipe (6); the ring balance (4) measures the aerodynamic force and aerodynamic moment of the spray pipe (6); the corrugated pipe (20) deforms along with the ring balance (4), and seals and isolates the high-pressure air source airflow in the airflow channel (18) of the ventilating support rod, so that the high-pressure air source airflow is prevented from influencing the measurement of the ring balance (4); the pressure range of the high-pressure air source is 5MPa to 8MPa.
2. The nozzle thrust measurement test system with the integrated design of the afterbody and the nozzle as claimed in claim 1, wherein the nozzle deflection angle α is in the range of-20 °.
3. The nozzle thrust measurement test system with the integrated design of the afterbody and the nozzle as claimed in claim 1, characterized in that the windward side of the ventilating vane (2) is provided with an arc windward side for rectification.
4. The nozzle thrust measurement test system with the integrally designed afterbody and nozzle as claimed in claim 1, characterized in that the front end of the venting strut (3) is closed by a closure cap (8); the blocking cover (8) is a step cylinder, and the diameter of the front section cylinder of the blocking cover (8) is smaller than that of the rear section cylinder; the rear section of the cylinder of the blocking cover (8) is inserted into the front end of the ventilating support rod (3); the front section cylinder of the blocking cover (8) extends out of the ventilating support rod (3), and the cutting sleeve (10) is sleeved on the front section cylinder of the blocking cover (8); the rear end of the cutting sleeve (10) is provided with a circular groove matched with the front end head of the ventilation support rod (3), the rear end face of the cutting sleeve (10) is a contact face of the cutting sleeve (10) and the front end face of the ventilation blade (2), and the front end of the cutting sleeve (10) is provided with a locking nut (9); the locking nut (9) is screwed down, the clamping sleeve (10) is tightly pressed against the front end face of the ventilating blade (2), and the plugging cover (8) and the clamping sleeve (10) are fixed;
the fairing (7) is sleeved on the clamping sleeve (10) and wraps the blocking cover (8), the locking nut (9) and the clamping sleeve (10), and the spherical outer surface of the fairing (7) faces to incoming flow and is used for incoming flow rectification.
5. The nozzle thrust measurement test system with the integrally designed afterbody and nozzle as claimed in claim 4, wherein the inner wall of the cutting sleeve (10) is provided with a sealing ring I (11) for sealing the contact surface of the cutting sleeve (10) and the front section cylinder of the blanking cap (8); the rear end face of the cutting sleeve (10) is provided with a sealing ring II (12) for sealing the contact surface of the rear end face of the cutting sleeve (10) and the front end face of the ventilating blade (2); a sealing ring III (13) is arranged on the rear section of the cylinder of the blocking cover (8) and used for sealing the contact surface of the blocking cover (8) and the inner wall of the ventilation support rod (3); a sealing ring IV (14) is arranged at the front section of the ventilation support rod (3) and is used for sealing the contact surface of the ventilation support rod (3) and the rear end surface of the ventilation blade (2); the front end of the corrugated pipe (20) is provided with a sealing ring V (15) for sealing the contact surface between the inner layer mounting surface at the rear end of the ventilating support rod (3) and the front end of the corrugated pipe (20), and the front end of the corrugated pipe (20) is also provided with the sealing ring V (15) for sealing the contact surface between the inner layer mounting surface at the front end of the aircraft rear body (5) and the rear end of the corrugated pipe (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211388071.4A CN115436009B (en) | 2022-11-08 | 2022-11-08 | Jet pipe thrust measurement test system with integrally designed afterbody and jet pipe |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211388071.4A CN115436009B (en) | 2022-11-08 | 2022-11-08 | Jet pipe thrust measurement test system with integrally designed afterbody and jet pipe |
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| CN115436009A true CN115436009A (en) | 2022-12-06 |
| CN115436009B CN115436009B (en) | 2023-01-31 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116202774A (en) * | 2023-04-28 | 2023-06-02 | 中国航发四川燃气涡轮研究院 | Exhaust full-containment structure for high-altitude bench vector test |
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